A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.


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    Titel :

    Load relief control of launch vehicle using aerodynamic angle estimation


    Beteiligte:
    Oh, Gyeongtaek (Autor:in) / Park, Jongho (Autor:in) / Park, Jeongha (Autor:in) / Lee, Hongju (Autor:in) / Kim, Youdan (Autor:in) / Shin, Sang-Joon (Autor:in) / Ahn, Jaemyung (Autor:in) / Cho, Sangbum (Autor:in)


    Erscheinungsdatum :

    01.06.2018


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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